Results
2000-16-14: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200, -300, and -300F series airplanes. This AD requires either an inspection to detect damage or chafing of the insulation or wires, modification of the cable assembly, and repairs, if necessary; or replacement of the cable assembly of the lower anti-collision light with a new cable assembly. This amendment is prompted by reports of electrical arcing on structure near the lower body anti-collision light due to chafing of the cable. The actions specified by this AD are intended to prevent such chafing as a result of improper installation of the lower body anti-collision light assembly, which could result in electrical arcing or sparking in a flammable leakage zone of the airplane.
2000-16-16: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes, that currently requires a one-time inspection to determine the serial numbers of various switch modules on the overhead panel and control stand, and replacement of certain switch modules with new, improved modules. That AD also requires repetitive tests of the cargo fire extinguishing system, and one-time tests of the fuel crossfeed valve, pack, trim air, and alternate flap control switches; and repair or replacement of switch modules with new improved modules, if necessary. This amendment revises the applicability of the existing AD. This action also requires replacement of the existing switch modules with new switch modules; replacement of the existing module assemblies with new module assemblies; or reworked module assemblies; as applicable. This amendment is prompted by the FAA's determination that certain switches are susceptible to contamination. The actions specified by this AD are intended to minimize contamination of the switch contacts and consequent failure of the switches, which, if not corrected, could result in inability of the flight crew to activate the cargo fire extinguishing, fuel, air conditioning, and alternate flap systems.
2015-21-09: We are superseding Airworthiness Directive (AD) 2015-19-02 for all The Boeing Company Model 767 airplanes. AD 2015-19-02 required revising the maintenance or inspection program to include new airworthiness limitations. This AD continues to require a maintenance or inspection program revision, but with revised language. This AD was prompted by a determination that certain language in the airworthiness limitation was not accurate in AD 2015-19-02. We are issuing this AD to detect and correct latent failures of the fuel shutoff valve to the engine and auxiliary power unit (APU), which could result in the inability to shut off fuel to the engine and APU and, in case of certain fires, an uncontrollable fire that could lead to structural failure.
2010-20-12: We are adopting a new airworthiness directive (AD) for Model 747-400, 747-400D, and 747-400F series airplanes. This AD requires installing a hot short protector (HSP) for the fuel quantity indicating system (FQIS) of the center fuel tank and, for certain airplanes, the horizontal stabilizer fuel tank. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent an electrical hot short from a source outside the FQIS to the densitometer wiring from causing failure of the FQIS densitometer resistors, which could result in an ignition source inside the center or horizontal stabilizer fuel tanks. An ignition source, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. This AD is effective November 5, 2010.\n\n The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of November 5, 2010.
2000-16-13: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace HP137 Mk1, Jetstream series 200, and Jetstream Models 3101 and 3201 airplanes. This AD requires you to inspect the nose wheel steering system to assure that the free play between the steering handle or knob and the nose wheels is within acceptable limits, and requires you to adjust the free play as necessary. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent the inability to steer the airplane because of excessive free play in the steering linkage. This excessive free play could then result in loss of control of the airplane during take-off, landing, or taxi operations.
98-16-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires revising the Airplane Flight Manual (AFM) to require use of the electrical fuel pump for take-off and landing and performance of an operational check of the electrical fuel pump following landing. This amendment also requires replacement of the jet booster pumps with new or modified jet booster pumps, which terminates the requirement for the AFM revision. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the jet booster pumps, which could result in reduced engine thrust during take-off or landing, and consequent increased risk of impact with terrain.
77-16-04: 77-16-04 HAWKER SIDDELEY AVIATION, LTD: Amendment 39-2996 applies to de Havilland Model DH-104 "Dove" airplanes, all series, certificated in all categories. Compliance is required as indicated. To prevent possible fatigue failure of the wing structure, accomplish the following: (a) Irrespective of the incorporation of Hawker Siddeley Aviation, Ltd., (HSA) Modification 539, for wings which have not had HSA Modification 780 incorporated, within the next 25 hours time in service after the effective date of this AD or prior to accumulation of 3400 hours total time in service on the wing lower spar boom, whichever occurs later, at intervals not to exceed 3400 hours time in service, on the boom, replace it with a serviceable boom of the same part number or an FAA-approved equivalent. (b) For wings which incorporate HSA Modification 780, replace the wing lower spar boom with a serviceable boom of the same part number or an FAA-approved equivalent - (1) For Series1A, 2A, 5A, 5BA, 6A airplanes, prior to the accumulation of 20,000 hours total time in service on the wing lower spar boom including the time in service prior to incorporation of the modification; and (2) For Series 7A and 8A airplanes, prior to the accumulation of 16,000 hours total time in service on the boom including the time in service prior to incorporation of the modification. (c) For airplanes which do not incorporate HSA Modification 538 in the area of the fuselage center section, or have Modification 538 incorporated but not the associated HSA Modification 686, within the next 25 hours time in service after the effective date of this AD or prior to the accumulation of 1800 hours total time in service on the fuselage center section lower spar boom whichever occurs later, and thereafter, at intervals not to exceed 1800 hours time in service on the boom, replace the fuselage center section lower spar boom with a serviceable boom of the same part number or an FAA-approved equivalent. (d) For airplanes which incorporate HSA Modification 538 in the area of the fuselage center section, provided the associated HSA Modification 686 has been incorporated within 3600 hours time in service on the fuselage center section lower spar boom since incorporating Modification 538, within the next 25 hours time in service on the boom after the effective date of this AD or prior to the accumulation of 6700 hours total time in service on the fuselage center section lower spar boom, including time in service prior to incorporation of the modification, whichever occurs later, and thereafter at intervals not to exceed 6700 hours time in service, replace the fuselage center section lower spar boom with a serviceable boom of the same part number or an FAA-approved equivalent. NOTE: For airplanes which incorporate HSA Modification 779 in the area of the fuselage center section, no mandatory retirement time is imposed on the fuselage center section lower spar boom. (e) Upon the request of an operator, the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East region may adjust a replacement interval specified in paragraphs (a), (c), or (d) of this AD, if the request contains substantiating data to indicate that the average operating spectrum of the particular airplane is less severe than the operating spectrum upon which the specified replacement times are based and that the adjustment requested is justified. Forward request to FAA, Chief, Aircraft Certification Staff, c/o American Embassy, APO New York, N.Y. 09667. NOTE: Appendix 1 of HSA Technical New Sheet (TNS) No. 119, Issue 10, dated July 19, 1971, contains information with respect to data needed to determine an average operating spectrum. (f) Unless already accomplished, on airplanes converted to series 7AXC or 8AXC in accordance with HSA TNS No. 181, Issue 3, dated November 21, 1966, replace the wings prior to the accumulation of one fifth the total hourstime in service at conversion plus 16,000 hours time in service as determined in accordance with the instructions in paragraph 7 of HSA TNS No. 181, Issue 3, dated November 21, 1966, or an FAA-approved equivalent. (g) Operators who have not kept records of time in service on any component to which a provision of this AD applies shall substitute airplane hours time in service in lieu thereof. This amendment supersedes Amendment 289 to Part 507 of the Regulations of the Administrator (26 FR 4395), AD 61-11-03, as amended by Amendment 585 (28 FR 7394) and Amendment 662 (28 FR 14238). This amendment becomes effective August 31, 1977.
2022-22-02: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, EC 155B, and EC155B1 helicopters. This AD was prompted by reports of the cockpit doors failing to open after ditching with inflated floats on certain helicopters equipped with an emergency flotation system (EFS). This AD requires revising the existing Rotorcraft Flight Manual (RFM) for your helicopter, installing placards, and depending on your model helicopter, modification of the jettisoning system, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2010-20-07: The FAA is adopting a new airworthiness directive (AD) for all International Aero Engines AG (IAE) V2500-A1, V2525-D5 and V2528-D5 turbofan engines and certain serial numbers (S/Ns) of IAE V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 turbofan engines. For certain S/Ns of V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5, V2530-A5, and V2533-A5 series turbofan engines, this AD requires initial and repetitive on-wing ultrasonic inspections of the high-pressure compressor (HPC) stage 3 to 8 drum for cracks. As mandatory terminating action to the repetitive inspections, this AD requires removal from service of the fully silver plated nuts attaching the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum, removal of silver residue from the HPC stage 3 to 8 drum, and fluorescent penetrant inspection (FPI) of the stage 3 to 8 drum within a specified time. For all other engines, this AD requires removal from service of the fully silver plated nuts attaching the HPC stage 3 to 8 drum to the HPC stage 9 to 12 drum, removal of silver residue from the HPC stage 3 to 8 drum, and FPI of the HPC stage 3 to 8 drum at the next drum piece-part exposure. This AD results from reports of 39 HPC stage 3 to 8 drums found cracked since March 2009. We are issuing this AD to prevent uncontained failure of the HPC stage 3 to 8 drum, which could result in damage to the airplane.
2000-16-03: This amendment adopts a new airworthiness directive (AD), applicable to all Bombardier Model DHC-7-100, and DHC-8-100, -200, and -300 series airplanes, that requires a one-time inspection of maintenance records to determine the method used during the most recent weight and balance check of the airplane and, if necessary, accomplishment of a weight and balance check. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent unusual handling characteristics and consequent reduced controllability during ground operations due to incorrect methods of weighing and balancing the airplane.
2022-21-14: The FAA is superseding Airworthiness Directive (AD) 2017-10- 17, which applied to certain Airbus SAS Model A330-200; A330-200 Freighter; and A330-300 series airplanes. AD 2017-10-17 required revising the existing maintenance or inspection program, as applicable, to incorporate new fuel airworthiness limitations. This AD was prompted by a determination that new or more restrictive fuel airworthiness limitations and tasks are necessary. This AD continues to require the actions in AD 2017-10-17 and requires revising the existing maintenance or inspection program, as applicable, to incorporate additional new or more restrictive fuel airworthiness limitations and tasks, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also expands the applicability to include additional airplane models. The FAA is issuing this AD to address the unsafe condition on these products.
2022-21-07: The FAA is adopting a new airworthiness directive (AD) for all Deutsche Aircraft GmbH (Type Certificate Previously Held by 328 Support Services GmbH; AvCraft Aerospace GmbH; Fairchild Dornier GmbH; Dornier Luftfahrt GmbH) Model 328-100 and -300 airplanes. This AD was prompted by a safety analysis that lithium batteries installed in the personal electronic devices (PED) are a potential risk of an in-flight fire in the flight deck stowage boxes. This AD requires installing a placard and stowing the fire gloves on the left-hand (LH) flap door of the flight deck step; and installing the placards on the LH and right-hand (RH) flight deck stowage boxes. This AD also requires revising the operator's existing airplane flight manual (AFM) to include emergency procedures, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2006-06-03: The FAA is adopting a new airworthiness directive (AD) for certain Cessna Model 500, 501, 550, S550, 551, and 560 airplanes. This AD requires revising the airplane flight manual (AFM) to prohibit use of the wing fuel boost pumps for defueling under certain conditions; installing a placard; doing other specified investigative and corrective actions as necessary; and modifying the boost pumps. This AD also requires the subsequent removal of the AFM revision and placard. This AD results from a report of a chafed electrical wiring harness, which was arcing inside the fuel tank. We are issuing this AD to prevent potential fuel vapor ignition in a fuel tank, which could result in explosion and loss of the airplane.
98-21-30: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 series airplanes and all Model A310 and A300-600 series airplanes, that requires repetitive inspections for wear damage of the aft attachment fittings of the articulated seats and dummy tracks in the passenger compartment; and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct wear damage of the aft attachment fittings of the articulated seats and dummy tracks. Such wear damage could cause the floor panels to sag and result in failure of flight control systems and consequent reduced controllability of the airplane.
76-15-05: 76-15-05 CANADAIR: Amendment 39-2676 as amended by Amendment 39-3181. Applies to all CL-44D4 and CL-44J airplanes, certificated in all categories. Compliance required as indicated unless already accomplished. Affects the nose landing gear retraction actuator lever attachment bolts. (a) On airplanes with nose landing gear retraction actuator lever attachment bolts, P/N 44-85279, installed: (1) Within the next 250 landings after the effective date of this AD, accomplish the following: (i) Replace bolts with unused vacuum cadmium plated Voi-Shan bolts, P/N V.S.2738, or equivalent bolts. Voi-Shan bolts are identified by part number impression on the bolt head. (ii) Install V.S.2738 bolts in accordance with paragraph 4.1(e) through 4.1(h) of Canadair Service Information Circular No. 387-CL44, Issue 2, (SIC) or an equivalent installation. (b) On airplanes with V.S.2738 bolts installed: (1) Within the next 25 landings after the effective date of this airworthiness directive, accomplish the following: (i) Inspect V.S.2738 bolts in accordance with paragraph 4.1(a) through 4.1(c) of the SIC, or an equivalent inspection, for cracks, corrosion, pitting, or rework by chrome plating. (ii) Replace bolts showing signs of any of the above defects, before further flight, with unused V.S.2738 bolts, and install in accordance with paragraph 4.1(c) thru 4.1(h) of the SIC or approved equivalent procedure. (2) Vacuum cadmium plated V.S.2738 bolts, found free from defects, may be reinstalled provided: (i) Within the next 500 hours in service or 125 landings, whichever occurs first, after reinstallation and thereafter, at intervals not to exceed 500 hours in service or 125 landings from the last inspection, the bolts are inspected for cracks by magnetic particle inspection or eddy current inspection or an equivalent procedure. (ii) Reinstalled bolts that have attained 5000 hours in service or 1250 landings, must be replaced with unused V.S.2738 bolts or equivalent bolts, and installed in accordance with paragraph 4.1(c) thru 4.1(h) of the SIC or approved equivalent procedure. (iii) The repetitive inspection required by paragraph (b)(2)(i) may be discontinued when the used bolts are replaced with unused vacuum cadmium plated V.S.2738 bolts or equivalent bolts and installed in accordance with paragraph 4.1(c) thru 4.1(h) of the SIC, or approved equivalent procedure. (c) Unused vacuum cadmium plated Voi-Shan bolts, installed in accordance with paragraph (a)(1)(ii), must be replaced with unused bolts of the same type and installed in the same manner, at or before 13,500 hours in service or eight years, whichever occurs first. If bolts are removed prior to the aforementioned life limits, they must be inspected and installed in accordance with paragraph (b)(1)(i) and (ii). (d) Equivalent inspections, installations, bolts, and service information circular revisions, must be approved by theChief, Engineering and Manufacturing Branch, FAA, Eastern Region. (e) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance time specified in this AD. Amendment 39-2676 was effective July 28, 1976. This amendment 39-3181 is effective April 17, 1978.
2015-18-03: We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. TPE331-5, -5A, -5AB, -5B, -10, -10R, -10U, -10UF, -10UG, -10UGR, and -10UR model turboprop engines. This AD was prompted by engine propeller shaft coupling failures, leading to unexpected propeller pitch changes causing increased aerodynamic and asymmetric drag on the airplanes using these engines. This AD requires removing certain part number (P/N) engine propeller shaft couplings from service. This AD also requires inserting a copy of certain airplane operating procedures into applicable flight manuals. We are issuing this AD to prevent loss of airplane control, leading to an accident.
2009-09-03R1: We are revising an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Since issuance of AD 2007-0109, Turbom ca has released modification TU166 which consists in inserting HP blade dampers between the HP disc and the HP blade platform. Introduction of these dampers has demonstrated to limit axial displacement of the HP blade relative to the disk in case of blade lock rupture or opening, therefore eliminating the need for inspection and replacement. We are issuing this AD to prevent an uncommanded in-flight engine shutdown which could result in an emergency autorotation landing or an accident.
89-22-09: 89-22-09 CASA: Amendment 39-6363. Docket No. 89-NM-111-AD. Applicability: Model C-212 series airplanes equipped with a passenger entry step installed under Supplemental Type Certificate (STC) SA906GL, certificated in any category. Compliance: Required within 60 days after the effective date of this AD, unless previously accomplished. To prevent delay in opening the passenger door in the event of an emergency evacuation, accomplish the following: A. Remove the step, handrails, door latch modifications, and associated hardware installed in accordance with Fischer Brothers Aviation, Inc., Installation Instructions for FBD-206, Revision F, dated June 5, 1985. B. Restore the door handle to the original CASA configuration. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Chicago Aircraft Certification Office, ACE-115C, FAA, Central Region. NOTE:The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment, and then send it to the Manager, Chicago Aircraft Certification Office, ACE-115C. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. The applicable service information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Chicago Aircraft Certification Office, 2300 East Devon Avenue, Des Plaines, Illinois. This amendment (39-6363, AD 89-22-09) becomes effective November 20, 1989.
2000-16-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Saab Model SAAB 340B and SAAB 2000 series airplanes, that currently requires various inspections of fluorescent lamps and lampholders in the cabin area for discrepancies; corrections, if necessary; and reinspection of the lamps to ensure correct installation after replacement or reinstallation of the lamps. This amendment requires replacement of the electronic light ballasts with improved ballasts, which terminates the reinspections, and expands the applicability of the existing AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent electrical arcing between the fluorescent tube pins and the lampholders, which could burn the surrounding area and lead to smoke and fumes in the passenger compartment or lavatory area.
93-14-13: 93-14-13 TEXTRON LYCOMING: Amendment 39-8637. Docket 91-ANE-55. Applicability: Textron Lycoming ALF502R and ALF502L turbofan engines installed on but not limited to British Aerospace BAe-146 and Canadair Challenger CL600 aircraft. Compliance: Required as indicated, unless accomplished previously. To prevent third stage turbine disk failure, which could result in engine shutdown, accomplish the following: (a) For ALF502R series engines with installed third stage turbine rotor shaft assemblies, Part Number (P/N) 2-143-040-12, P/N 2-143-040-15, or P/N 2-143-040-16, rework the third stage turbine disk blade slots and mark the third stage turbine assembly with a new part number in accordance with the Accomplishment Instructions of Textron Lycoming Service Bulletin (SB) No. ALF502R 72-270, dated March 31, 1992, or replace with a serviceable part as follows: (1) For third stage turbine disks with 15,000 or more cycles in service (CIS) on the effective date of this AD, within 1,000 CIS after the effective date of this AD. (2) For third stage turbine disks with 10,000 or more CIS but less than 15,000 CIS on the effective date of this AD, within 1,000 CIS, after the effective date of this AD, or at the next shop visit, whichever occurs later, but prior to accumulating 16,000 CIS since new. (3) For third stage turbine disks with less than 10,000 CIS on the effective date of this AD, at the next blade removal, but prior to accumulating 13,000 CIS since new. (4) For third stage turbine disks not reworked in accordance with the requirements of this AD and installed on Textron ALF-502R engines as replacement disks when complying with this paragraph, accomplish the requirements of this paragraph as to that replacement disk. (b) For ALF502L series engines with installed third stage turbine rotor shaft assemblies, Part Number (P/N) 2-143-040-10, P/N 2-143-040-11, P/N 2-143-040-12, P/N 2-143-040-15, or P/N 2-143-040-16, rework the third stage turbine disk blade slots and mark the third stage turbine assembly with a new part number in accordance with the Accomplishment Instructions of Textron Lycoming SB ALF502L 72-270, dated April 30, 1993, or replace with a serviceable part as follows: (1) For third stage turbine disks with 15,000 or more CIS on the effective date of this AD, within 1,000 CIS after the effective date of this AD. (2) For third stage turbine disks with 10,000 or more CIS but less than 15,000 CIS on the effective date of this AD, within 1,000 CIS after the effective date of this AD or at the next shop visit, whichever occurs later, but prior to accumulating 16,000 CIS since new. (3) For third stage turbine disks with less than 10,000 CIS on the effective date of this AD, at the next blade removal, but prior to accumulating 13,000 CIS since new. (4) For third stage turbine disks not reworked in accordance with the requirements of this AD and installed on Textron Lycoming ALF-502L engines as replacement disks when complying with this paragraph, accomplish the requirements of this paragraph as to that replacement disk. (c) For the purpose of this AD, a shop visit is defined as the induction of an engine into a shop for maintenance. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The rework and reidentification shall be done in accordance with the following Textron Lycoming service bulletins: Document No. Pages Revision Date ALF502R 72-270 1-4 1 March 31, 1992 5 Original June 28, 1991 6-7 1 March 31, 1992 8-10 Original June 28, 1991 Total pages: 10 ALF502L 72-270 1-13 Original April 30, 1993 Total pages: 13 This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Textron Lycoming, 550 Main Street, Stratford, Connecticut 06497. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (g) This amendment becomes effective on October 4, 1993.
2015-21-01: We are adopting a new airworthiness directive (AD) for all Technify Motors GmbH TAE 125-02 reciprocating engines with a dual mass flywheel installed. This AD requires installation of a start phase monitoring system and associated specified software. This AD was prompted by reports of a gearbox drive shaft breaking during starting or restarting of the engine. We are issuing this AD to prevent overload and failure of the gearbox drive shaft, which could result in failure of the engine, in-flight shutdown, and loss of control of the airplane.
51-20-02: 51-20-02 MARTIN: Applies to All Models 202 and 202A Airplanes, Except as Noted. Compliance required as specified. In order to comply with recommendations of the Martin 202 Modification Board, the following items must be accomplished. In all cases, modifications which are demonstrated to provide a level of safety equivalent to that provided by the modifications listed herein will be acceptable in lieu of the listed modifications. 1. Compliance required not later than January 1, 1952. (a) Cover heater ignition interlock relay box tightly. (Applies to Model 202 airplanes only.) (b) Cover autopilot servo control relay box tightly. (Applies to Model 202 airplanes only.) (c) Cover AC distribution panel tightly or replace with enclosed relays. (d) Enclose all uncovered relays in the DC distribution panel in a box or replace with enclosed relays. (e) Cover heating and ventilating control box tightly. 2. Compliance required not later than November 15, 1951. Either replace present dural crossfeed line with a continuous piece of fire-resistant hose where it passes through the fuselage and relocate the fittings to a location outboard of the fuselage, or provide adequately drained liquid and vapor-proof shroud for the fuel crossfeed line where it passes through the main electrical compartment in the fuselage. (Glenn L. Martin Service Bulletin No. 173 covers one method of compliance with this item.) (Applies to Model 202 airplanes only.) 3. Compliance required not later than March 1, 1952. Make electrical hydraulic pump explosion proof. (Glenn L. Martin Service Bulletin No. 188, issued for the Model 202A, covers this same subject and may be used for both 202 and 202A airplanes.) 4. Compliance required not later than March 1, 1952. Install separate circuit breakers for the pitot tube heater circuits. (Glenn L. Martin Service Bulletin No. 118, issued for the Model 202A, covers this same subject and may be used for both 202 and 202A airplanes.) 5. Compliance required not later than March 1, 1952. Replace all 75ST aileron hinge fittings with steel parts. (Glenn L. Martin Maintenance Note No. 164 covers this same subject.) (Applies to Model 202 airplanes only.)
2000-16-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Industrie Model A300 B2 and B4 series airplanes, that currently requires inspection of the fuselage longitudinal lap joints and circumferential joints, and of the stringers and doublers for bonding delamination and cracks; and repairs, as necessary. This amendment requires expansions of certain inspection areas; revisions of certain inspection thresholds or intervals; changes in references to inspection methods; and the addition of a modification to certain longitudinal lap joints. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent delamination and cracking of the fuselage, which could result in rapid decompression of the airplane.
2015-21-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-102, -103, -106, -201, -202, -301, -311, and -315 airplanes. This AD was prompted by reports of un-annunciated failures of the direct current (DC) starter generator, which caused caution indicators of the affected systems to illuminate and prompted emergency descents and landings. This AD requires replacing the DC generator control units (GCUs) with new GCUs and replacing the GCU label. We are issuing this AD to prevent a low voltage condition on the left main DC bus, which, during critical phases of flight, could result in the loss of flight management, navigation, and transponder systems, and could affect continued safe flight.
92-19-08: 92-19-08 FAIRCHILD AIRCRAFT (formerly Swearingen Aviation Corporation): Amendment 39-8366. Docket No. 92-CE-09-AD. Supersedes AD 81-02-01, Amendment 39-4009. Applicability: The following model and serial numbered airplanes, certificated in any category: Model Serial Numbers SA226-T all serial numbers SA226-T(B) all serial numbers SA226-AT all serial numbers SA226-TC all serial numbers SA227-TT TT421 through TT444 SA227-AT AT423 through AT440 SA227-AC AC406, AC415, AC416, and AC420 through AC448 NOTE 1: The only SA227 series airplanes affected by this AD are those manufactured before the production change that incorporated rudder pedal links with bushings that more efficiently prevent wear. Compliance: Required upon the accumulation of 5,000 hours time-in-service (TIS) or within the next 50 hours TIS after the effective date of this AD, whichever occurs later, unless already accomplished within the last 5,000 hours TIS (superseded AD 81-02-01, Amendment 39-4009), and thereafter at intervals not to exceed 5,000 hours TIS. To prevent failure of the rudder cable to rudder pedal link attachments, which could result in loss of control of the airplane, accomplish the following: (a) Remove and discard the rudder cable to rudder pedal link attachment bolts and bushings, and prior to further flight, accomplish the following in accordance with the instructions in either Swearingen Aviation Corporation Service Bulletin (SB) 27-027, issued: July 17, 1980; or Fairchild SB 227-27-029, issued: June 6, 1991, whichever is applicable, and the applicable maintenance manual: (1) Inspect the rudder pedal links, part number 26-72016, for elongated holes. (2) Replace any rudder pedal links that have elongated holes. (3) Install new rudder pedal link attachment bolts and bushings. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location wherethe requirements of this AD can be accomplished. (c) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Airplane Certification Office, FAA, 4400 Blue Mound Road, Fort Worth, Texas 76193-0150. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth Airplane Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth Airplane Certification Office. (d) The inspections and modifications required by this AD shall be done in accordance with either Swearingen Aviation Corporation Service Bulletin 27-027, issued: July 17, 1980; or Fairchild Service Bulletin 227-27-029, issued: June 6, 1991, whichever is applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment (39-8366) supersedes AD 81-02-01, Amendment 39-4009. (f) This amendment becomes effective on October 16, 1992.